Compound projectile with separable sections



Jan. 27, 1959 2,870,710

COMPOUND PROJECTILE! WITH SEPARABLE SECTIONS R. E. MIEDEL Filed March10, 1954 IN VEN TOR. Roland E. Mie de=1 Attorneys United States PatentCOMPOUND PROJECTILE WITH SEPARABLE SECTIONS Roland E. Miedel, Hatboro,Pa.

Application March 10, 1954, Serial No. 415,452

6 Claims. (Cl. 102-50) (Granted under Title 35, U. S. Code (1952), see.266) The invention described herein may be manufactured and used by orfor the Government of the United States of America for governmentalpurposes without the payment of any royalties thereon or therefor.

This invention relates to a compound aerial projectile and moreparticularly to a projectile including separable forward and rearwardportions arranged to be launched attached together as a unit and totravel a substantial distance toward a target as a single unit andthereafter.

to be separated and spaced apart in flight so that they arrive at thesame target at spaced intervals.

It is well known that an attack upon a heavily protected military targetcan only succeed when a large number of projectiles strike the target asin the case of a salvo of projectiles fired substantiallysimultaneously, as is the case when batteries of guns are fired by avessel or when a large number of rockets are fired by an aircraft.However, this type of an attack has several disadvantages. First, eachindividual projectile must be directed accurately from the point atwhich it is launched to the target. Consequently, due to the manydiverse factors affecting the flight of each projectile, it isimpossible to control the trajectory of each projectile so closely thatthey all arrive at exactly the same point. Next, this limitation on theperformance of the various projectiles further limits the effectivenessof a salvo of individual projectiles when used against a well protectedtarget. Since the destructive effect of each individual projectile maybe substantially dissipated before it penetrates a protective layer suchas armor plate, a salvo of projectiles does not necessarily have acumulative destructive effect upon the target unless, by chance, two ormore projectiles strike the target at exactly the same spot so thatsuccessive projectiles may penetrate the target deeply through theweakened area or opening provided by the first projectile.

The present invention contemplates a means for directing a plurality ofprojectiles against a single target with the maximum effect. Thus, aprojectile embodying the novel features of the instant invention wouldcomprise a compound assembly including two or more interconnectedprojectile portions united together for launching and during most of theflight t0 the target and arranged to be separated and spaced apart inflight without being diverted from their original trajectory. With suchan arrangement the respective projectile portions, each provided with anindividual destructive charge, arrive at the same point on the target atclosely spaced intervals so that the respective destructive charges havea maximum cumulative effect upon the target.

An object of the present invention is the provision of means fordirecting a plurality of destructive charges from a common launchingsite to a given target so that they arrive at the target at spacedintervals.

Another object is to provide a compound projectile assembly including aplurality of separate portions attached together for launching as a unitand subsequently separable in flight.

Patented Jan. 27, 1959 A further object of the invention is theprovision of a compound projectile assembly including a plurality ofseparable portions each capable of sustained flight along apredetermined trajectory when separated from, the other portions of theassembly.

Still another object is to provide a compound projectile assemblyincluding a plurality of projectile portions at least one of which isprovided with means to cause that portion to become spaced apart fromanother portion when the respective portions are disconnected duringflight.

A final object of the present invention is the provision of a compoundprojectile assembly including a plurality of projectile portions atleast one of which is provided with propulsive means effective to drivethe projectile assembly toward a target from its launching site.

The exact nature of this invention as well as other objects andadvantages thereof will be readily apparent from consideration of thefollowing specification relating to the annexed drawing in which:

Fig. 1 shows a preferred embodiment of the forward projectile portion ofa compound projectile assembly.

Fig. 2 shows a preferred embodiment of the rearward projectile portionof a compound projectile assembly.v

Referring now to the drawings wherein like reference charactersdesignate like or corresponding parts throughout the several views,there is shown in Fig. l a pro jectile assembly 10 including anelongated body 11, sup porting air foil surfaces 12, stabilizing airfoil surfaces 13, a destructive charge 14 disposed within the bodyportion 11, a shaped recess 15 .in the rear end of the elongated bodyportion 11, and a first component of a latch mechanism, hereafterreferred to as the latch release, designated by the reference numeral 16and operatively connected by suitable means 17 to an automatic latchcontrol means 18 which may be either an automatic time control mechanismoperable after a predetermined time interval has elapsed or a suitableproximity sensing means arranged to be actuated by close proximity of atarget. Since the latch control means may be of any conventional designsuitable for incorporation in this device, the connecting means 17 maybe an electrical, mechanical, or hydraulic means, as required for theparticular latch control means selected.

The timer 18, the latch release- 16, and the connecting means 17therebetween illustrated schematically in Fig. 1, may, for example,comprise a purely mechanical system such as that illustrated in Fig. lof U. S. Patent No. 2,316,656, issued April 13, 1943, including apropeller attached to a threaded shaft 43, a tapered oamrming surface39, and a hollow rod 37 supporting camrning surface 39 and threadablyengaging shaft 43. Alternatively, they may comprise an electricallycontrolled system such as that illustrated in Fig. 5 of U. S. Patent No.2,654,320, issued October 6, 1953, including a timing control 51 capableof generating electrical impulses. an electrically actuated means forreleasing the bow and stem portions, and an electrical connection 53 fortransmitting the electrical impulse.

Referring now to Fig. 2 the showing therein comprises the rearwardprojectile portion of a compound projectile generally designated by thereference numeral 20 and including an elongated body 21, supporting airfoil surfaces 22, stabilizing air foil surfaces 23, a suitabledestructive charge 24, a second component 26 of a latch mechanism,hereafter referred to as the latch, located in the forward end of thebody 21 and arranged to co operate wit-h the latch release portion 16 ofthe latch mechanism mounted within the body portion 11. The respectiveconnecting means 27 *operatively interconnecting said second portion ofthe latch mechanisms and a 3 pair of actuator mechanisms 28 disposedadjacent to and operatively connected to a pair of aerodynamic brakingmeans 29.

The latch component 26, the aerodynamic braking means 29, the actuatormechanisms 28, and connecting means 27, illustrated schematically inFig. 2, may, for example, comprise a typical control system for draginducing flaps such as that illustrated schematically in U. S. PatentNo. 2,629,569, issued February 24, 1953, comprising the hydraulic valve64 controlled by the solenoid coil 58, the drag flaps 34, the hydraulicjack 35, and conduits 65 and 66, respectively.

In addition, the projectile portion shown in Fig. 2 may also include astorage tank 31 for a suitable propellant. conduit means 32, andpropulsion units 33, all operatively interconnected so that thepropellant contained in the tank 31 may be burned in the propulsionunits 33 to drive the projectile assembly toward its target.

While the concurrent operation of means for actuating the aerodynamicbraking means 29 may be controlled by any conventional operationinitiating means embodied in the second component 26 of the latchmechanism, the necessary initiating signal for actuating the aerodynamicbraking means 29 may be supplied directly from' the automatic latchcontrol means 18 by a suitable electrical connection thereto, in themanner illustrated in Fig. of the U. S. Patent No. 2,654,320, issuedOctober 6, 1953, wherein a timing control 51 concurrently actuateselements 47, 19 and 55 through electrical connections 52, 54 and 56traversing the releasable connection by means of which the respectiveportions of a severable aircraft are interconnected.

Operation of the present invention is as follows. Prior to launching thecompound missile composed of the forward projectile portion, shown inFig. 1, and the rearward projectile portion, shown in Fig. 2, therespective portions are releasably interconnected by inserting theforward end of the body 21 into the recess in the rearward end of thebody 11 to bring the portions 16 and 26 of the latch mechanism intooperative engagement so that the portion is securely attached to theportion 10 by the latch mechanism. Thereafter, the compound projectileassembly is launched as a unit from a suitable launching device eitheron the ground or on a moving ship or aircraft. The compound missile ispreferably self-propelled by means of a suitable propulsion device suchas a jet engine or rocket motors or the like which may be provided inone or more of the projectile portions. One suitable arrangement isshown in Fig. 2. The compound projectile assembly is guided along apredetermined trajectory by means of suitable supporting and stabilizingsurfaces such as those illustrated in Figs. 1 and 2 until it reaches aposition relatively close to the intended target. At this point the timedelay mechanism or target sensing device 18 operates to actuate thelatch release portion 16 of the latch mechanism interconnecting therespective projectile portions so that they are released from eachother. The latch mechanism including the latch release 16 and the secondcomponent 26, together comprising a releasable connecting means which ispreferably so arranged that its release in turn initiates operation ofthe actuators 28 which control suitable aerodynamic braking means 29mounted upon the rearward projectile portion so that the rearwardprojectile portion is slowed sufiiciently to be displaced a substantialdistance from the forward projectile portion without being diverted fromthe predetermined trajectory. Finally, the forward projectile portion 10strikes the target at a given point and the rearward projectile portion20 strikes the same point on the target after a short time interval haselapsed.

There are several critical design factors which must be taken intoaccount in constructing the present inven tion in order to insuresuccessful operation of this novel device. First, it is essential thatthe compound projectile assembly be arranged so that it is capable ofstable flight along a predetermined path when it is launched and flownas a single unit. Second, it is essential that each of the respectiveprojectile portions have a configuration such that it is capable ofstable flight along a predetermined trajectory when it is released fromand is traveling separately from the other projectile portion. One suchconfiguration is illustrated in Figs. 1 and 2. In this connection, it isdesirable that the respective destructive charges 14 and 24 each belocated at, or close to, the center of gravity of its respectiveprojectile portion. Furthermore, it is desirable that the storage tank31 be so located within the rearward projectile portion that it lies ator near the center of gravity of the compound projectile assembly whenthe respective projectile portions are interconnected as a unit in orderto minimize the adverse effect on the stability of the projectileassembly due to consumption of the propellant. Finally, it is importantto obtain the spaced relationship between the respective projectileportions by reducing the relative rate of travel of the rearwardprojectile portion rather than by forcibly separating the respectiveprojectile portions, in order to minimize the possibility of deflectingone or both of the projectile portions from its prescribed trajectorywhen they are separated. One such speed reducing system is illustratedas incorporated in the rearward projectile portion shown in Fig. 2.

Numerous variations both in specific structural details of the variousoperating components and in the external configuration of this deviceare possible, but since they are not significant to this invention theywill not be described in detail herein. Moreover, it should be notedthat many Variations in the nature of the destructive charges iscontemplated. One or both of these charges may be varied in order toachieve the maximum elfect on various types of targets. In fact, variousinterchangeable charges may be made available for use in this device inorder to facilitate making changes as desired. For example, for useagainst heavily armored targets such as battleships the forwardprojectile portion may be provided with an armor piercing charge whilethe rearward projectile portion is provided with an incendiary charge.With such an arrangement, the armor piercing charge would penetrate theprotective surface or the target and thereafter the incendiary chargewould pass through the opening provided by the first charge andpenetrate deeply within the target where it can be detonated for maximumeffect.

Ubviously many modifications and variations of the present invention arepossible in the light of the above teachings. It is therefore to beunderstood that within the scope of the appended claims the inventionmay be practiced otherwise than as specifically described.

What is claimed is:

1. An airborne compound projectile assembly comprising at least twoindividually aerodynamically stable elongated projectile sections eachcontaining a destructive charge therein, connecting means arranged torigidly interconnect said sections in axial alignment with complementarysurfaces interfitted and automatically releasable as the projectileassembly approaches a target, aerodynamic braking means initiallydisposed in a low drag position upon the rearmost section and movable toa high drag position, and positioning means operable when saidconnecting means is released to move said aerodynamic braking means tothe high drag position and thereby withdraw said rearmost section fromthe next adjacent section in flight, whereby said sections continuealong substantially the same trajectory to strike the same target atspaced intervals.

2. An airborne self-propelled compound projectile assembly comprising atleast two individually aerodynamically stable elongated sections eachcontaining a destructive charge, propulsion means mounted upon at leastone of said sections and arranged to propel said projectile assemblyalong a predetermined trajectory, connecting means arranged to rigidlyinterconnect said sections in axially aligned relationship withcomplementary surfaces interfitted and automatically releasable as theprojectile assembly closely approaches a target, aerodynamic brakingmeans initially disposed in a low drag position upon the rearmostsection and movable to a high drag position, and positioning meansoperable when said connecting means is released to withdraw saidrearmost section from the next adjacent section in flight, whereby saidsections continue along substantially the same trajectory to strike thesame target at spaced intervals.

3. A compound projectile comprising an aerodynamically stable forwardprojectile portion containing a first destructive charge, anaerodynamically stable rearward projectile portion containing a seconddestructive charge, releasable connecting means rigidly interconnectingsaid projectile portions with complementary interfitting surfaces inengagement, which connecting means is automatically releasable as theprojectile assembly closely approaches a target, aerodynamic brakingmeans mounted upon said rearward projectile portion for displacementfrom a low drag position to a high drag position, and actuator meansoperable when said connecting means is released to displace saidaerodynamic braking means from said low drag position to said high dragposition and thereby withdraw said rearward projectile portion from saidforward projectile portion in flight, whereby said sections continuealong substantially the same trajectory to strike the same target atspaced intervals.

4. A self-propelled compound projectile assembly comprising anaerodynamically stable forward projectile portion containing a firstdestructive charge, a rearward projectile portion containing a seconddestructive charge and also propulsive means for driving the projectileassembly along a predetermined trajectory, releasable connecting meansrigidly interconnecting said projectile portions with complementaryinterfitting surfaces in engagement, which connecting means isautomatically releasable as the projectile assembly closely approaches atarget, aerodynamic braking means mounted upon said rearward projectileportion for displacement from a low drag position to a high dragposition, and actuator means operable when said connecting means isreleased to displace said aerodynamic braking means from said low dragposition to said high drag position and thereby withdraw said rearwardprojectile portion from said forward projectile portion in flight,whereby said projectile portions continue along substantially the sametrajectory to strike the same target at spaced intervals.

5. An airborne compound projectile assembly, comprising a forwardsection including a first faired aerodynamically stable elongated bodyfitted with suitable lifting and stabilizing surfaces, a firstdestructive charge contained within the elongated body of said forwardsection, a rear section including a second faired aerodynamically stableelongated body fitted with suitable lifting and stabilizing surfaces andarranged to be releasably connected at interfitting surfaces to saidforward section in fixed axial alignment therewith for launching andinitial flight of the projectile assembly as an aerodynamically stableunit, a second destructive charge contained within the body of said rearsection, releasable connecting means for rigidly interconnecting therearward end of said forward section and the forward end of said rearsection, control means automatically operable to release said connectingmeans when the projectile closely approaches a target, aerodynamicbraking means mounted upon said rear section and movable from aretracted low drag position to an extended high drag position, andactuator means operable simultaneously with the release of saidconnecting means to move said aerodynamic braking means from saidretracted position to said extended position and thereby slow down saidrear section relative to said forward section to completely disengagesaid forward section and said rearward section so that the respectivesections continue along the same flight path and arrive at a giventarget at spaced intervals.

6. An airborne self-propelled compound projectile assembly, comprising aforward section including a first faired aerodynamically stableelongated body fitted with suitable lifting and stabilizing surfaces, afirst destructive charge contained in said forward section, a rearsection including a second faired aerodynamically stable elongated bodyfitted with suitable stabilizing and lifting surfaces, a seconddestructive charge contained Within the body of said rear section, apropulsive means for the compound projectile assembly mounted in therear end of the body of said rear section, releasable connecting meansfor rigidly interconnecting the rearward end of said forward section andthe forward end of said rearward section at interfitting surfaces sothat said sections are attached together in fixed axial alignment forlaunch ing and initial flight of the projectile assembly as anaerodynamically stable unit, control means automatically operable torelease said connecting means when the projectile closely approaches thetarget, areodynamic braking means mounted upon said rear section andmovable from a retracted low drag position to an extended high dragposition, and actuator means operable simultaneously with the release ofsaid connecting means to move said aerodynamic braking means from saidretracted position to said extended position and thereby slow down saidrear section relative to said forward section to completely disengagesaid sections so that the respective sections are spaced apart in flightas they continue along a common flight path to the target.

References Cited in the file of this patent UNITED STATES PATENTS1,838,035 Elia Dec. 22, 1931 2,246,429 Brandt June 17, 1941 2,316,656Walker Apr. 13, 1943 2,455,845 Wells Dec. 7, 1948 2,654,320 Schmid Oct.6, 1953 FOREIGN PATENTS 115,388 Sweden Feb. 17, 1948 680,803 GreatBritain Oct. 15, 1952

